论文部分内容阅读
基于雷诺平均Navier-Stokes(RANS)方程和结构网格技术,采用五阶空间离散精度的加权紧致非线性格式(WCNS)和剪切应力输运(SST)两方程湍流模型,开展了DLR-F6和DLR-F6_FX2B2种翼身组合体构型的高阶精度数值模拟,计算外形来自AIAA第三届阻力预测研讨会。主要目的是确认WCNS模拟跨声速典型运输机构型和预测局部构型变化引起的气动特性变化量的能力。在固定升力系数条件下,采用粗、中、细3套网格开展了网格收敛性研究,从气动力系数、压力系数分布、表面流态等方面研究了网格规模对DLR-F6和DLR-F6_FX2B翼身组合体数值模拟结果的影响;采用中等网格开展了来流迎角对2种翼身组合体气动特性的影响研究。通过与National Transonic Facility(NTF)的试验结果和CFL3D的计算结果对比,表明采用高阶精度计算方法得到了网格收敛的数值模拟结果,较好地模拟了DLR-F6翼身组合体局部修型引起的微小气动特性变化和翼身结合部流动特性的差异。
Based on the Reynolds-averaged Navier-Stokes (RANS) equation and the structural grid technique, two-equation turbulent models of weighted exact nonlinear (WCNS) and shear stress transport (SST) F6 and DLR-F6_FX2B2 wing-body combination of high-end precision numerical simulation, the calculated shape from the AIAA third resistance prediction seminar. The main purpose is to confirm the ability of the WCNS to simulate transonic typical transport mechanisms and to predict changes in aerodynamic characteristics due to local configuration changes. Under the conditions of fixed lift coefficient, the mesh convergence is studied by using three sets of coarse, medium and fine grids. The effects of grid size on the DLR-F6 and DLR are studied from the aspects of aerodynamic coefficient, pressure coefficient distribution and surface flow. -F6_FX2B wing-body combination. The influence of the incoming angle of attack on the aerodynamic characteristics of the two wing-body combinations was studied by using a medium mesh. Comparing with the results of National Transonic Facility (NTF) and those of CFL3D, it shows that the numerical simulation results of grid convergence are obtained by using high-order precision calculation method, and the local modification of DLR-F6 wing body assembly is well simulated Caused by changes in the small aerodynamic characteristics and wing junction flow characteristics of the difference.